CN107010232A - A kind of double dynamical unmanned plane - Google Patents
A kind of double dynamical unmanned plane Download PDFInfo
- Publication number
- CN107010232A CN107010232A CN201710413123.1A CN201710413123A CN107010232A CN 107010232 A CN107010232 A CN 107010232A CN 201710413123 A CN201710413123 A CN 201710413123A CN 107010232 A CN107010232 A CN 107010232A
- Authority
- CN
- China
- Prior art keywords
- battery case
- unmanned plane
- battery
- double dynamical
- motor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000007789 sealing Methods 0.000 claims description 12
- 230000006835 compression Effects 0.000 claims description 9
- 238000007906 compression Methods 0.000 claims description 9
- 229910052751 metal Inorganic materials 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 7
- 230000005611 electricity Effects 0.000 claims description 6
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 238000005183 dynamical system Methods 0.000 claims description 2
- 230000007257 malfunction Effects 0.000 abstract description 4
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000006866 deterioration Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Battery Mounting, Suspending (AREA)
Abstract
The invention discloses a kind of double dynamical unmanned plane, including the unmanned plane with remote control function, the unmanned plane has hybrid power system, the hybrid power system includes the first battery case and the second battery case, a power supply selection control is provided with unmanned mainboard, it selects the first battery case or the second battery case as the supply power supply of unmanned plane by the remote control control at land end, an ejection mechanism is provided with one side end face of first battery case and the second battery case, another end opening of first battery case and the second battery case, an independent small-sized motor is provided with first battery case and the second battery case, a rotor is provided with the motor shaft of motor.The present invention may be selected one of battery case and be powered for unmanned plane, when fortuitous events such as one of cell malfunctions, burnings, can promptly eject the battery of damage, in order to avoid causing damage to fuselage, mitigates fuselage and bears a heavy burden.
Description
Technical field
The present invention relates to unmanned plane field, and in particular to a kind of double dynamical unmanned plane.
Background technology
At present, unmanned plane has caused the common concern and great attention of sciemtifec and technical sphere, function in multi-field extensive use
Various, the numerous and diverse unmanned plane equipment of pattern is emerged in an endless stream, and high application value has been embodied in numerous technical fields, application
Field includes agriculture and forestry, geologic prospect, take photo by plane photography, data acquisition, even military investigation etc..Although unmanned plane species is numerous
Many, function is different, but the application of all unmanned planes and function are built on the dynamic foundation of unmanned plane, and existing unmanned plane
The power of equipment far can not meet use demand, and it is a great problem of unmanned plane research and development that the cruising time of unmanned plane is short.
When in use, if unmanned plane works overloadingly, the heat of battery is very big for the battery of unmanned plane, and nobody
The most important part of machine is battery compartment, and battery overheat is easily burnt, blast or it is on fire, situations such as leak etc., therefore very
When many under severe conditions, what is first gone wrong is typically all the battery of power section, if one of battery is let out
When a series of uncertain situations of leakage, burning, overheat, short circuit etc. occur, problem is not solved now, then next can trigger
More serious the problem of, therefore we must reasonably be separated at the appropriate time, and the battery gone wrong is gone out to ejection,
It is prevented to be continuing with influenceing the normal flight of unmanned plane.
The content of the invention
The technical problems to be solved by the invention are to provide a kind of optional one of battery case and powered for unmanned plane, when
During the fortuitous events such as one of cell malfunctions, burning, the battery of damage can be promptly ejected, in order to avoid fuselage is caused to damage
Wound, mitigates fuselage and bears a heavy burden.
The present invention is achieved through the following technical solutions：A kind of double dynamical unmanned plane, including with remote control work(
The unmanned plane of energy, the unmanned plane has hybrid power system, and the hybrid power system includes the first battery case and the second battery case,
First battery case or the second battery case are powered for unmanned plane, and a power supply selection control is provided with unmanned mainboard
Device, it selects the first battery case or the second battery case as the supply power supply of unmanned plane by the remote control control at land end,
An ejection mechanism, the first battery case and are provided with one side end face of first battery case and the second battery case
An independent small-sized driving electricity is provided with another end opening of two battery cases, the first battery case and the second battery case
It is provided with machine, the motor shaft of motor on a rotor, rotor and is mounted on a sealing blade, the sealing runner sealing electricity
The openend of pond box.
As preferred technical scheme, the ejection mechanism includes being arranged in the first battery case and the second battery case
Compression spring, one end of the compression spring is provided with a supporting pad, and the supporting pad is pressed on battery by compression spring
On lead accumulator end face in box, the other end of lead accumulator is contacted with sealing vane end faces.
As preferred technical scheme, the internal cell intracavitary of first battery case and the second battery case is provided with
Metal contact piece, the electrode of lead accumulator is connected conduction with metal contact piece, and lead accumulator is provided with two strands of power lines, the first power line
The host computer control component of unmanned plane is connected, second source line connects small-sized motor, powered to small-sized motor, small-sized drive
The control end of dynamic motor connects the host computer control component of unmanned plane, and host computer control component receives control by radio receiving transmitting module and referred to
Order, drives small-sized motor work.
As preferred technical scheme, first battery case and the second battery case are made of aluminum alloy materials.
The beneficial effects of the invention are as follows：The present invention may be selected one of battery case and be powered for unmanned plane, when one of
During the fortuitous events such as cell malfunctions, burning, the battery of damage can be promptly ejected, in order to avoid causing damage to fuselage, is mitigated
Fuselage bears a heavy burden.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is the accompanying drawing used required in technology description to be briefly described, it should be apparent that, drawings in the following description are only this
Some embodiments of invention, for those of ordinary skill in the art, on the premise of not paying creative work, can be with
Other accompanying drawings are obtained according to these accompanying drawings.
Fig. 1 is overall structure diagram of the invention.
Embodiment
All features disclosed in this specification, or disclosed all methods or during the step of, except mutually exclusive
Feature and/or step beyond, can combine in any way.
Any feature disclosed in this specification (including any accessory claim, summary and accompanying drawing), except non-specifically is chatted
State, can alternative features equivalent by other or with similar purpose replaced.I.e., unless specifically stated otherwise, each feature
It is an example in a series of equivalent or similar characteristics.
As shown in figure 1, including the unmanned plane with remote control function, the unmanned plane has hybrid power system, described double
Dynamical system includes the first battery case 1 and the second battery case 9, and the first battery case 1 or the second battery case 9 supply for unmanned plane
A power supply selection control is provided with electricity, unmanned mainboard, it selects the first battery by the remote control control at land end
The battery case 9 of box 1 or second is used as the supply power supply of unmanned plane, a side of the battery case 9 of the first battery case 1 and second
Be provided with another end opening of an ejection mechanism, the first battery case and the second battery case on face, the first battery case and
It is provided with second battery case on an independent small-sized motor 5, the motor shaft of motor 5 and is provided with a rotor 6,
A sealing blade 8 is mounted on rotor 6, the openend of the sealed cell box of blade 8 is sealed.
Wherein, ejection mechanism includes the compression spring 7 being arranged in the first battery case and the second battery case, compresses bullet
One end of spring 7 is provided with a supporting pad (not shown), and supporting pad is pressed on the lead accumulator end in battery case by compression spring
On face, the other end of lead accumulator is contacted with sealing vane end faces.
In the present embodiment, the internal cell intracavitary of the first battery case 1 and the second battery case 9 is provided with metal contact piece 2,
The electrode of lead accumulator is connected conduction with metal contact piece, and lead accumulator is provided with two strands of power lines, and the first power line 3 connects nobody
The host computer control component of machine, second source line 4 connects small-sized motor, is powered to small-sized motor, small-sized motor
Control end connect unmanned plane host computer control component, host computer control component pass through radio receiving transmitting module receive control instruction, drive
Dynamic small-sized motor work.Due to the assembling mode using metal contact piece and electrode so that losing the branch of sealing blade
After support, lead accumulator can be ejected out of battery cavities at once, due to the battery for useless damage, be further continued for being arranged on nobody
In machine, then the deterioration of unmanned plane is easily lead to
In the present embodiment, the first battery case 1 and the second battery case 9 are made of aluminum alloy materials.We are by setting
Two battery cases are put, give unmanned plane to provide electric energy, the electricity in one of battery case by one of them of two battery cases
When pond occurs unexpected, we can operate remote manipulator, control one of them small-sized motor work, and then open originally
By the opening of closure runner sealing, lead battery can so be ejected by the elastic force of compression spring, it is very practical.
The beneficial effects of the invention are as follows：The present invention may be selected one of battery case and be powered for unmanned plane, when one of
During the fortuitous events such as cell malfunctions, burning, the battery of damage can be promptly ejected, in order to avoid causing damage to fuselage, is mitigated
Fuselage bears a heavy burden.
The foregoing is only a specific embodiment of the invention, but protection scope of the present invention is not limited thereto, any
The change or replacement expected without creative work, should all be included within the scope of the present invention.Therefore, it is of the invention
Protection domain should be determined by the scope of protection defined in the claims.
Claims (4)
1. a kind of double dynamical unmanned plane, it is characterised in that：Including the unmanned plane with remote control function, the unmanned plane has double
Dynamical system, the hybrid power system includes the first battery case and the second battery case, first battery case or the second electricity
Pond box is powered for unmanned plane, and a power supply selection control is provided with unmanned mainboard, and it passes through the remote control control at land end
System the first battery case of selection or the second battery case are used as the supply power supply of unmanned plane, first battery case and the second battery
Another end opening of an ejection mechanism, the first battery case and the second battery case, first are provided with one side end face of box
It is provided with an independent small-sized motor, the motor shaft of motor and is provided with battery case and the second battery case
A sealing blade, the openend of the sealing runner sealing battery case are mounted on one rotor, rotor.
2. double dynamical unmanned plane as claimed in claim 1, it is characterised in that：The ejection mechanism includes being arranged at the first electricity
Compression spring in pond box and the second battery case, one end of the compression spring is provided with a supporting pad, and the supporting pad leads to
Overcompression spring compression is on the lead accumulator end face in battery case, and the other end of lead accumulator is contacted with sealing vane end faces.
3. double dynamical unmanned plane as claimed in claim 1, it is characterised in that：First battery case and the second battery case
Internal cell intracavitary is provided with metal contact piece, and the electrode of lead accumulator is connected conduction with metal contact piece, and lead accumulator is provided with
Two strands of power lines, the first power line connects the host computer control component of unmanned plane, and second source line connects small-sized motor, to small
Type motor is powered, and the control end of small-sized motor connects the host computer control component of unmanned plane, and host computer control component passes through
Radio receiving transmitting module receives control instruction, drives small-sized motor work.
4. double dynamical unmanned plane as claimed in claim 1, it is characterised in that：First battery case and the second battery case are equal
It is made of aluminum alloy materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710413123.1A CN107010232A (en) | 2017-06-05 | 2017-06-05 | A kind of double dynamical unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710413123.1A CN107010232A (en) | 2017-06-05 | 2017-06-05 | A kind of double dynamical unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107010232A true CN107010232A (en) | 2017-08-04 |
Family
ID=59452236
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710413123.1A Pending CN107010232A (en) | 2017-06-05 | 2017-06-05 | A kind of double dynamical unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107010232A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109835474A (en) * | 2017-11-27 | 2019-06-04 | 智飞智能装备科技东台有限公司 | A kind of unmanned plane of four axis, eight rotor overlapping dynamical system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20140136749A (en) * | 2013-05-21 | 2014-12-01 | 한국과학기술연구원 | Power system of unmanned aerial vehicle using liquid hydrogen |
| CN105253306A (en) * | 2015-11-09 | 2016-01-20 | 杨珊珊 | UAV (Unmanned aerial vehicle) provided with falling guard device and falling guard method thereof |
| CN205801535U (en) * | 2016-06-16 | 2016-12-14 | 深圳市科比特航空科技有限公司 | A kind of blast resistance construction of unmanned plane fuel cell |
| CN206194832U (en) * | 2016-12-07 | 2017-05-24 | 深圳市加贝智能科技有限公司 | Retinue unmanned aerial vehicle battery compartment structure |
| CN106697302A (en) * | 2017-03-10 | 2017-05-24 | 太仓韬信信息科技有限公司 | Safe launching device of hydrogen cell of UAV (Unmanned Aerial Vehicle) |
-
2017
- 2017-06-05 CN CN201710413123.1A patent/CN107010232A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20140136749A (en) * | 2013-05-21 | 2014-12-01 | 한국과학기술연구원 | Power system of unmanned aerial vehicle using liquid hydrogen |
| CN105253306A (en) * | 2015-11-09 | 2016-01-20 | 杨珊珊 | UAV (Unmanned aerial vehicle) provided with falling guard device and falling guard method thereof |
| CN205801535U (en) * | 2016-06-16 | 2016-12-14 | 深圳市科比特航空科技有限公司 | A kind of blast resistance construction of unmanned plane fuel cell |
| CN206194832U (en) * | 2016-12-07 | 2017-05-24 | 深圳市加贝智能科技有限公司 | Retinue unmanned aerial vehicle battery compartment structure |
| CN106697302A (en) * | 2017-03-10 | 2017-05-24 | 太仓韬信信息科技有限公司 | Safe launching device of hydrogen cell of UAV (Unmanned Aerial Vehicle) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109835474A (en) * | 2017-11-27 | 2019-06-04 | 智飞智能装备科技东台有限公司 | A kind of unmanned plane of four axis, eight rotor overlapping dynamical system |
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| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170804 |
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| RJ01 | Rejection of invention patent application after publication |